CA2781710A1 - Fuel cell system and method for drying of exhaust gas of a fuel cell system - Google Patents
Fuel cell system and method for drying of exhaust gas of a fuel cell system Download PDFInfo
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- CA2781710A1 CA2781710A1 CA2781710A CA2781710A CA2781710A1 CA 2781710 A1 CA2781710 A1 CA 2781710A1 CA 2781710 A CA2781710 A CA 2781710A CA 2781710 A CA2781710 A CA 2781710A CA 2781710 A1 CA2781710 A1 CA 2781710A1
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- Prior art keywords
- fuel cell
- cell system
- cooling element
- detachment device
- gas
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- 239000000446 fuel Substances 0.000 title claims abstract description 51
- 238000001035 drying Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims description 17
- 238000001816 cooling Methods 0.000 claims abstract description 92
- 239000007789 gas Substances 0.000 claims abstract description 69
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 65
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 11
- 239000002828 fuel tank Substances 0.000 claims description 11
- 239000001257 hydrogen Substances 0.000 claims description 11
- 229910052739 hydrogen Inorganic materials 0.000 claims description 11
- 238000007790 scraping Methods 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims 2
- 238000002844 melting Methods 0.000 claims 1
- 230000008018 melting Effects 0.000 claims 1
- 239000002826 coolant Substances 0.000 description 9
- 239000003570 air Substances 0.000 description 7
- 239000012080 ambient air Substances 0.000 description 7
- 239000007788 liquid Substances 0.000 description 6
- 230000006872 improvement Effects 0.000 description 5
- 239000012528 membrane Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000007710 freezing Methods 0.000 description 3
- 230000008014 freezing Effects 0.000 description 3
- JEGUKCSWCFPDGT-UHFFFAOYSA-N h2o hydrate Chemical compound O.O JEGUKCSWCFPDGT-UHFFFAOYSA-N 0.000 description 3
- 230000008929 regeneration Effects 0.000 description 3
- 238000011069 regeneration method Methods 0.000 description 3
- 238000009877 rendering Methods 0.000 description 3
- 241000894006 Bacteria Species 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000007791 dehumidification Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000012263 liquid product Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
- H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
- H01M8/04119—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying
- H01M8/04156—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying with product water removal
- H01M8/04164—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying with product water removal by condensers, gas-liquid separators or filters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/26—Drying gases or vapours
- B01D53/265—Drying gases or vapours by refrigeration (condensation)
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D2259/00—Type of treatment
- B01D2259/45—Gas separation or purification devices adapted for specific applications
- B01D2259/4566—Gas separation or purification devices adapted for specific applications for use in transportation means
- B01D2259/4575—Gas separation or purification devices adapted for specific applications for use in transportation means in aeroplanes or space ships
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
- B64D2041/005—Fuel cells
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- General Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Thermal Sciences (AREA)
- Analytical Chemistry (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Electrochemistry (AREA)
- Fuel Cell (AREA)
Abstract
The invention relates to a fuel cell system having a device for drying gases, comprising at least one cooling body having at least one first surface and at least one removal device. The cooling body is designed to be thermally connected to a heat sink and make contact with gas flowing past. The removal device is displaceably mounted relative to the first surface and is set up for removing frozen water from the first surface. Gases are thereby dried, wherein continuous drying having a simultaneously constant drying result can take place over a long period of time.
Description
Fuel cell system and method for drying of exhaust gas of a fuel cell system RELATED APPLICATIONS:
The present application claims priority of German patent application No. 10 2009 051 212.8, filed 29 October 2009 and of United States provisional patent application No.
61/256,015, filed 29 October 2009, the disclosures of which are incorporated herein by reference.
TECHNICAL FIELD:
The invention relates to a fuel cell system with an apparatus for drying exhaust gases of the fuel cell system, to a method for drying exhaust gases of a fuel cell system and to an aircraft with at least one such fuel cell system.
BACKGROUND OF THE INVENTION:
For modern commercial aircraft, occasionally fuel cell systems are conceived or already used in order to handle various tasks. Apart from electricity generation, other tasks can also be carried out, for example rendering a fuel tank inert by introducing the exhaust gases of a fuel cell system. Because of the way a fuel cell operates, the exhaust gas usually contains water vapor. Generally-speaking, if humid gases are used for rendering a fuel tank inert, there is a problem in that fuels, in particular kerosene, are hygroscopic.
Furthermore, there is a danger that moreover a bacteria population can form in the tank, which bacteria population could influence sensors for acquiring the fill level of the tank so that acquisition becomes imprecise. Furthermore, within the fuel tank or the fuel itself, ice crystals could form that could result in damage to engine injection nozzles and fuel filters in cruising flight of the aircraft or during below-zero temperatures on the ground. There is thus a requirement for introducing dry gases into the fuel tank in order to be able to render the fuel tank inert.
DE 10 2005 054 885 Al and US 2007/0111060 Al disclose a safety system for reducing the danger of explosion of a fuel tank, in which system a protective-gas production device comprises a fuel cell system with a fuel cell, and provides a protective gas which during operation of the fuel cell system is produced by the fuel cell.
In prior art various methods and systems are known which are used for drying gases, in
The present application claims priority of German patent application No. 10 2009 051 212.8, filed 29 October 2009 and of United States provisional patent application No.
61/256,015, filed 29 October 2009, the disclosures of which are incorporated herein by reference.
TECHNICAL FIELD:
The invention relates to a fuel cell system with an apparatus for drying exhaust gases of the fuel cell system, to a method for drying exhaust gases of a fuel cell system and to an aircraft with at least one such fuel cell system.
BACKGROUND OF THE INVENTION:
For modern commercial aircraft, occasionally fuel cell systems are conceived or already used in order to handle various tasks. Apart from electricity generation, other tasks can also be carried out, for example rendering a fuel tank inert by introducing the exhaust gases of a fuel cell system. Because of the way a fuel cell operates, the exhaust gas usually contains water vapor. Generally-speaking, if humid gases are used for rendering a fuel tank inert, there is a problem in that fuels, in particular kerosene, are hygroscopic.
Furthermore, there is a danger that moreover a bacteria population can form in the tank, which bacteria population could influence sensors for acquiring the fill level of the tank so that acquisition becomes imprecise. Furthermore, within the fuel tank or the fuel itself, ice crystals could form that could result in damage to engine injection nozzles and fuel filters in cruising flight of the aircraft or during below-zero temperatures on the ground. There is thus a requirement for introducing dry gases into the fuel tank in order to be able to render the fuel tank inert.
DE 10 2005 054 885 Al and US 2007/0111060 Al disclose a safety system for reducing the danger of explosion of a fuel tank, in which system a protective-gas production device comprises a fuel cell system with a fuel cell, and provides a protective gas which during operation of the fuel cell system is produced by the fuel cell.
In prior art various methods and systems are known which are used for drying gases, in
-2-particular air. Thus it would, for example, be possible to carry out adsorption by means of hygroscopic media, for example silica gel. However, the water absorption capacity of a hygroscopic medium is finite, and consequently after use it would have to either be replaced or regenerated. In particular in an aircraft, replacement leads to pronounced weight problems, and constant emptying and refilling leads to increased maintenance effort.
Furthermore, regeneration would be possible by means of a corresponding heat input, for example by means of heated air. However, this would place in doubt the effectiveness of the fuel cell system, because thermal regeneration would require considerable expenditure of energy. If no regeneration is to be carried out, due to the above-mentioned saturation, exhaust gas drying is possible only for a limited period of time. Generally speaking, in such methods dew points, i.e. temperatures, are attained at which there is a state of equilibrium between condensing water and evaporating water, which dew points or temperatures reach far into the double-digit negative region.
A further method for drying air takes place by water transfer by means of a selective membrane, with the use of a partial pressure differential. To this effect a membrane would be used that separates a gas to be dried from a dry gas, wherein, due to a partial pressure differential, water is made to pass through the membrane. As an alternative to the dry gas it would also be possible to increase the static pressure on that membrane side on which the gas to be dried is located. The drying performance of this method is limited by the achievable partial pressure differential. Particularly low dew points of a membrane compressed-air dryer are only achieved with the use of quite a high operating pressure and the accompanying high compressor performance necessary.
A further, third, method from prior art for gas drying would take place by cooling the gas to below the dew point, for which purpose basically only a heat exchanger and a heat sink or a cooling medium are required. Following cooling, and for final separation of liquid water from gaseous residual gas, a drip catcher or the like could be used. However, this principle requires quite considerable cooling capacity because liquid product water is present, and the energy released during the phase transition needs to be discharged. The cold used to cool the gas can in part be recovered in a downstream recuperative heat exchanger.
Basically, in this arrangement the attainable dew point is limited by the freezing point, because in the design
Furthermore, regeneration would be possible by means of a corresponding heat input, for example by means of heated air. However, this would place in doubt the effectiveness of the fuel cell system, because thermal regeneration would require considerable expenditure of energy. If no regeneration is to be carried out, due to the above-mentioned saturation, exhaust gas drying is possible only for a limited period of time. Generally speaking, in such methods dew points, i.e. temperatures, are attained at which there is a state of equilibrium between condensing water and evaporating water, which dew points or temperatures reach far into the double-digit negative region.
A further method for drying air takes place by water transfer by means of a selective membrane, with the use of a partial pressure differential. To this effect a membrane would be used that separates a gas to be dried from a dry gas, wherein, due to a partial pressure differential, water is made to pass through the membrane. As an alternative to the dry gas it would also be possible to increase the static pressure on that membrane side on which the gas to be dried is located. The drying performance of this method is limited by the achievable partial pressure differential. Particularly low dew points of a membrane compressed-air dryer are only achieved with the use of quite a high operating pressure and the accompanying high compressor performance necessary.
A further, third, method from prior art for gas drying would take place by cooling the gas to below the dew point, for which purpose basically only a heat exchanger and a heat sink or a cooling medium are required. Following cooling, and for final separation of liquid water from gaseous residual gas, a drip catcher or the like could be used. However, this principle requires quite considerable cooling capacity because liquid product water is present, and the energy released during the phase transition needs to be discharged. The cold used to cool the gas can in part be recovered in a downstream recuperative heat exchanger.
Basically, in this arrangement the attainable dew point is limited by the freezing point, because in the design
-3-currently in widespread use icing occurring within the heat exchanger can result in the blocking of gas ducts.
SUMMARY OF THE INVENTION:
Correspondingly, it may be considered an object of the invention to propose a system for cooling the exhaust gas of a fuel cell system, which system for cooling reduces or entirely eliminates the above-mentioned disadvantages.
In particular it may be considered an object of the invention to propose a system for drying exhaust gas of a fuel cell system, which system for drying with the use of as little energy as possible makes it possible to dry the exhaust gas as effectively as possible without significantly increasing the complexity of the fuel cell system or its periphery, while at the same time minimizing the additional weight.
The object may be met by a fuel cell system having an apparatus for drying of exhaust gas of the fuel cell system according to the independent claim 1. Advantageous improvements are stated in the subordinate claims.
According to a first aspect of the invention, the apparatus for drying of exhaust gas of the fuel cell system comprises at least one cooling element with at least one first surface and at least one detachment device.
The cooling element is designed to be thermally connected to a heat sink and to come into contact with gas flowing past the first surface. In concrete terms this means that a cooling element of any shape can be connected in any desired manner with a heat sink in order to be cooled. In this arrangement connection with the heat sink can be carried out in completely different ways. For example, a cooling circuit could be provided that conducts a cooling medium as a heat sink through the cooling element so that heat from the cooling element is dissipated to the cooling medium. At the same time the cooling element could also be designed to establish a mechanical connection with a Peltier element or the like as a heat sink so that, as a result of contact with a cold side of a Peltier element, heat dissipation from
SUMMARY OF THE INVENTION:
Correspondingly, it may be considered an object of the invention to propose a system for cooling the exhaust gas of a fuel cell system, which system for cooling reduces or entirely eliminates the above-mentioned disadvantages.
In particular it may be considered an object of the invention to propose a system for drying exhaust gas of a fuel cell system, which system for drying with the use of as little energy as possible makes it possible to dry the exhaust gas as effectively as possible without significantly increasing the complexity of the fuel cell system or its periphery, while at the same time minimizing the additional weight.
The object may be met by a fuel cell system having an apparatus for drying of exhaust gas of the fuel cell system according to the independent claim 1. Advantageous improvements are stated in the subordinate claims.
According to a first aspect of the invention, the apparatus for drying of exhaust gas of the fuel cell system comprises at least one cooling element with at least one first surface and at least one detachment device.
The cooling element is designed to be thermally connected to a heat sink and to come into contact with gas flowing past the first surface. In concrete terms this means that a cooling element of any shape can be connected in any desired manner with a heat sink in order to be cooled. In this arrangement connection with the heat sink can be carried out in completely different ways. For example, a cooling circuit could be provided that conducts a cooling medium as a heat sink through the cooling element so that heat from the cooling element is dissipated to the cooling medium. At the same time the cooling element could also be designed to establish a mechanical connection with a Peltier element or the like as a heat sink so that, as a result of contact with a cold side of a Peltier element, heat dissipation from
-4-the cooling element to the Peltier element, and thus cooling, can take place.
Furthermore, it could also be possible to link a cold fluid as a heat sink from any source in any desirable manner with the cooling element so that, as a result of the low temperature of the fluid, cooling of the cooling element takes place. In this arrangement, for example, particularly cold ambient air from the surroundings of an aircraft in cruising flight could be considered, which air can be used either directly or by way of a heat exchanger implemented in the form of an outer-skin cooler. Likewise, the use of liquid hydrogen from a cryogenic tank could be considered as a heat sink, which hydrogen is used as fuel for the fuel cell.
In order to operate a fuel cell it is necessary anyway to convert the hydrogen from its liquid form to a gaseous form so that a heat input could be advantageous.
Such a cooling element provides an advantage in that the content of water or water vapor of a gas flowing past the first surface of the cooling element freezes and collects on the first surface. With an adequately cold temperature of the cooling element below the freezing point and adequate impingement of the first surface with the gas to be dried, adequate drying of the gas is possible.
The above-mentioned detachment device is movably held relative to the first surface of the cooling element and is designed to detach water that has frozen onto the first surface, and consequently no excessive deposit of ice occurs. This aspect of the invention is not limited to a particular type of detachment device; instead, here too any imaginable detachment devices can be considered. Mechanical detachment elements can be implemented that by means of scraping elements, scraping edges or the like, engage the first surface and mechanically detach ice from the first surface.
The specific disadvantages associated with the devices known from prior art can be overcome by the apparatus for drying included in the fuel cell system according to the invention. The use of a mechanical detachment device provides a particular advantage in that no saturation effects occur. Furthermore, no special materials need to be fed to the apparatus, which materials would allow the detachment of ice or drying of the gas.
Furthermore, a compact design can be anticipated.
Furthermore, it could also be possible to link a cold fluid as a heat sink from any source in any desirable manner with the cooling element so that, as a result of the low temperature of the fluid, cooling of the cooling element takes place. In this arrangement, for example, particularly cold ambient air from the surroundings of an aircraft in cruising flight could be considered, which air can be used either directly or by way of a heat exchanger implemented in the form of an outer-skin cooler. Likewise, the use of liquid hydrogen from a cryogenic tank could be considered as a heat sink, which hydrogen is used as fuel for the fuel cell.
In order to operate a fuel cell it is necessary anyway to convert the hydrogen from its liquid form to a gaseous form so that a heat input could be advantageous.
Such a cooling element provides an advantage in that the content of water or water vapor of a gas flowing past the first surface of the cooling element freezes and collects on the first surface. With an adequately cold temperature of the cooling element below the freezing point and adequate impingement of the first surface with the gas to be dried, adequate drying of the gas is possible.
The above-mentioned detachment device is movably held relative to the first surface of the cooling element and is designed to detach water that has frozen onto the first surface, and consequently no excessive deposit of ice occurs. This aspect of the invention is not limited to a particular type of detachment device; instead, here too any imaginable detachment devices can be considered. Mechanical detachment elements can be implemented that by means of scraping elements, scraping edges or the like, engage the first surface and mechanically detach ice from the first surface.
The specific disadvantages associated with the devices known from prior art can be overcome by the apparatus for drying included in the fuel cell system according to the invention. The use of a mechanical detachment device provides a particular advantage in that no saturation effects occur. Furthermore, no special materials need to be fed to the apparatus, which materials would allow the detachment of ice or drying of the gas.
Furthermore, a compact design can be anticipated.
-5-In an advantageous improvement of the apparatus, the detachment device comprises an edge that is designed to scrape off ice from the first surface of the cooling element. The edge is thus preferably to be designed in such a manner that its shape corresponds to the shape of the first surface. For example, if the first surface is a planar straight surface, a planar and straight-line edge could be used to scrape ice from the first surface. In this manner the quantity of ice that has accumulated on the first surface is always limited.
Consequently, continuous adequate heat dissipation for the icing of water vapor of the gas is possible.
According to an equally advantageous improvement of the apparatus, the cooling element is a hollow body, wherein the first surface is an inside surface of the cooling element. In this manner, in particular, the introduction and the passing-through of gas is simplified because the cooling element by its hollow shape could practically represent an air line. By thermally connecting the cooling element with a heat sink, ice collects on the inside surface of the cooling element, wherein this ice can be scraped off continuously, step-by-step or in an alternating manner.
Equally advantageous is the design of the cooling element in concrete terms as a body that at least in some sections is of a hollow-cylindrical shape, because this variant is particularly easy to manufacture, and can thus reduce the costs for producing the apparatus to a low level.
With the use of a hollow cooling element, particularly with a design that at least in some sections comprises a hollow-cylindrical shape, in an advantageous improvement of the apparatus it makes sense to use a spindle-shaped detachment device whose outer spindle edges are in contact with the inside surface of the cooling element. The spindle-shaped detachment device is preferably to be rotatably held on an axis that corresponds to the axis of extension of the cooling element. This concentric symmetric design makes possible uniform scraping-off on the entire inside surface. By means of continuous rotation of this spindle-shaped detachment device, which could, for example, comprise a helical scraping edge, ice is continuously scraped off the inside surface of the cooling element so that depending on the pitch and the number of helical turns of the detachment device the ice is removed immediately after it has collected on the inside of the cooling element.
Consequently, continuous adequate heat dissipation for the icing of water vapor of the gas is possible.
According to an equally advantageous improvement of the apparatus, the cooling element is a hollow body, wherein the first surface is an inside surface of the cooling element. In this manner, in particular, the introduction and the passing-through of gas is simplified because the cooling element by its hollow shape could practically represent an air line. By thermally connecting the cooling element with a heat sink, ice collects on the inside surface of the cooling element, wherein this ice can be scraped off continuously, step-by-step or in an alternating manner.
Equally advantageous is the design of the cooling element in concrete terms as a body that at least in some sections is of a hollow-cylindrical shape, because this variant is particularly easy to manufacture, and can thus reduce the costs for producing the apparatus to a low level.
With the use of a hollow cooling element, particularly with a design that at least in some sections comprises a hollow-cylindrical shape, in an advantageous improvement of the apparatus it makes sense to use a spindle-shaped detachment device whose outer spindle edges are in contact with the inside surface of the cooling element. The spindle-shaped detachment device is preferably to be rotatably held on an axis that corresponds to the axis of extension of the cooling element. This concentric symmetric design makes possible uniform scraping-off on the entire inside surface. By means of continuous rotation of this spindle-shaped detachment device, which could, for example, comprise a helical scraping edge, ice is continuously scraped off the inside surface of the cooling element so that depending on the pitch and the number of helical turns of the detachment device the ice is removed immediately after it has collected on the inside of the cooling element.
-6-Particularly advantageously the cooling element is enclosed by a further body, which on its inside forms a gap to the cooling element. Through such a gap a cooling medium could enter that results in cooling of the cooling element. The temperature of the inflowing cooling medium or the like should comprise a value that is adequately lower than 0 C.
In this respect the invention is not limited to a particular type of cooling medium;
instead, a number of different cooling media could be used. Both liquid and gaseous cooling media could be considered, wherein, in the use in an aircraft, ambient air from a ram air inlet or the like could also be suitable as a cooling medium, at least in cruise flight.
According to an equally advantageous improvement of the apparatus, a hollow-shaped cooling element on at least on one end comprises an opening-out shape so that the introduction of the gas to be dried and/or the discharge of the detached ice are/is facilitated.
The opening-out shape could, for example, be designed so as to be funnel-shaped or trumpet-shaped and could serve as a reservoir for ice or meltwater.
In an opening-out region of a hollow cooling element an aperture could be arranged through which the detached ice or the meltwater obtained from the outside in the frozen phase by the action of heat can be discharged. In this arrangement the action of heat can be implemented by the inflowing gas. In this arrangement the cooling element is preferably positioned in such a manner that mixing of the outflowing gas with the water to be discharged can be prevented. The apparatus could, for example, prevent this by horizontal support, because accumulated ice or accumulated meltwater could fall out or drip off perpendicularly to the direction of flow of the gas.
With the use of a spindle-shaped detachment device a drive device could be used that is arranged as far as possible outside axes of extension of the cooling element and of the detachment device so that the incident flow over the first surface of the cooling element is not impeded. For example an electrical motor, optionally with a suitable gear arrangement, could be selected as a suitable drive, wherein the invention is not, however, limited to the use of an electric motor. Instead, in particular in an aircraft environment, a pneumatic or hydraulic drive device could also be considered. With the use of a planar first surface, linear
In this respect the invention is not limited to a particular type of cooling medium;
instead, a number of different cooling media could be used. Both liquid and gaseous cooling media could be considered, wherein, in the use in an aircraft, ambient air from a ram air inlet or the like could also be suitable as a cooling medium, at least in cruise flight.
According to an equally advantageous improvement of the apparatus, a hollow-shaped cooling element on at least on one end comprises an opening-out shape so that the introduction of the gas to be dried and/or the discharge of the detached ice are/is facilitated.
The opening-out shape could, for example, be designed so as to be funnel-shaped or trumpet-shaped and could serve as a reservoir for ice or meltwater.
In an opening-out region of a hollow cooling element an aperture could be arranged through which the detached ice or the meltwater obtained from the outside in the frozen phase by the action of heat can be discharged. In this arrangement the action of heat can be implemented by the inflowing gas. In this arrangement the cooling element is preferably positioned in such a manner that mixing of the outflowing gas with the water to be discharged can be prevented. The apparatus could, for example, prevent this by horizontal support, because accumulated ice or accumulated meltwater could fall out or drip off perpendicularly to the direction of flow of the gas.
With the use of a spindle-shaped detachment device a drive device could be used that is arranged as far as possible outside axes of extension of the cooling element and of the detachment device so that the incident flow over the first surface of the cooling element is not impeded. For example an electrical motor, optionally with a suitable gear arrangement, could be selected as a suitable drive, wherein the invention is not, however, limited to the use of an electric motor. Instead, in particular in an aircraft environment, a pneumatic or hydraulic drive device could also be considered. With the use of a planar first surface, linear
-7-guiding of a detachment device could be considered that requires a corresponding linear guide gear arrangement on the drive device. At the same time it would make sense to arrange a corresponding gear arrangement on the motor in order to reduce the rotational speed and to increase the torque of a spindle-shaped detachment device.
The object is, furthermore, also met by a method for gas drying, which method essentially comprises the following steps. In the first instance a gas stream that is to be dried is directed onto a first surface of a cooling element; by means of a thermal connection with a heat sink the cooling element is cooled in order to, in this process, freeze the water vapor or water content contained in the gas, so that said water vapor or water content accumulates on the first surface. At the same time, subsequently or alternatingly, a detachment device on the first surface is moved so that the ice that has accumulated on the first surface is removed.
Optionally, removed ice is collected in a reservoir, and, furthermore optionally, is melted by exposure to external heat. The ice collected in the reservoir can fall out of it or can be discharged from it; likewise the ice that has optionally been melted by exposure to heat can be channeled out.
BRIEF DESCRIPTION OF THE DRAWINGS:
Further characteristics, advantages and application options of the present invention are disclosed in the following description of the exemplary embodiments and of the figures. All the described and/or illustrated characteristics per se and in any combination form the subject of the invention, even irrespective of their composition in the individual claims or their interrelationships. Furthermore, identical or similar components in the figures have the same reference characters.
Fig. 1 shows a diagrammatic view of a first exemplary embodiment of the apparatus according to the invention.
Fig. 2 shows a diagrammatic view of a second exemplary embodiment of the apparatus according to the invention.
The object is, furthermore, also met by a method for gas drying, which method essentially comprises the following steps. In the first instance a gas stream that is to be dried is directed onto a first surface of a cooling element; by means of a thermal connection with a heat sink the cooling element is cooled in order to, in this process, freeze the water vapor or water content contained in the gas, so that said water vapor or water content accumulates on the first surface. At the same time, subsequently or alternatingly, a detachment device on the first surface is moved so that the ice that has accumulated on the first surface is removed.
Optionally, removed ice is collected in a reservoir, and, furthermore optionally, is melted by exposure to external heat. The ice collected in the reservoir can fall out of it or can be discharged from it; likewise the ice that has optionally been melted by exposure to heat can be channeled out.
BRIEF DESCRIPTION OF THE DRAWINGS:
Further characteristics, advantages and application options of the present invention are disclosed in the following description of the exemplary embodiments and of the figures. All the described and/or illustrated characteristics per se and in any combination form the subject of the invention, even irrespective of their composition in the individual claims or their interrelationships. Furthermore, identical or similar components in the figures have the same reference characters.
Fig. 1 shows a diagrammatic view of a first exemplary embodiment of the apparatus according to the invention.
Fig. 2 shows a diagrammatic view of a second exemplary embodiment of the apparatus according to the invention.
-8-Figs 3a and 3b show diagrammatic views of two cooling options for the apparatus according to the invention.
Fig. 4 shows a diagrammatic view of the method according to the invention.
Fig. 5 shows an aircraft with at least one fuel cell and at least one apparatus according to the invention for drying the exhaust gas of the layer composition.
DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS:
Fig. 1 shows a schematic diagram of the basic principle of the apparatus for drying exhaust gas of a fuel cell system. A cooling element 2 of any desired shape (for the sake of simplicity only shown in sections in the diagram) is cooled by means of a connection with a heat sink (not shown in the diagram). The temperature of the cooling element 2 is below 0 C so that freezing or sublimation of water vapor in a gas 4 to be dried can be achieved.
The cooling element 2 comprises a first surface 6, along which the gas 4 to be dried flows.
The gas 4 comprises a defined content of water or water vapor that is to be discharged. As a result of the gas 4 flowing along the first surface 6 of the cooling element 2, the water freezes or sublimates and accumulates as a layer of ice on the first surface 6. The accumulation of ice cannot be carried out indefinitely, and for this reason a detachment device 8 is used that is held so as to be movable relative to the cooling element 2. For example, the detachment device 8 comprises a scraping edge 10 that is in contact with the first surface 6. As a result of the scraping edge 10 moving along the first surface 6, the ice is scraped off. With continuous movement of the detachment device 8 along the first surface 6, said surface 6 can always remain free of ice so that an ideal cooling effect can always act on the water content of the gas 4, and consequently continuous, ideal, dehumidification of the gas 4 can be carried out.
Fig. 2 shows a more concrete exemplary embodiment of the apparatus 11. In this arrangement a cooling element 12 is designed as a hollow cylinder through which the gas 4 to be dried flows. With adequate cooling, the first surface 14, designed as an inside surface
Fig. 4 shows a diagrammatic view of the method according to the invention.
Fig. 5 shows an aircraft with at least one fuel cell and at least one apparatus according to the invention for drying the exhaust gas of the layer composition.
DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS:
Fig. 1 shows a schematic diagram of the basic principle of the apparatus for drying exhaust gas of a fuel cell system. A cooling element 2 of any desired shape (for the sake of simplicity only shown in sections in the diagram) is cooled by means of a connection with a heat sink (not shown in the diagram). The temperature of the cooling element 2 is below 0 C so that freezing or sublimation of water vapor in a gas 4 to be dried can be achieved.
The cooling element 2 comprises a first surface 6, along which the gas 4 to be dried flows.
The gas 4 comprises a defined content of water or water vapor that is to be discharged. As a result of the gas 4 flowing along the first surface 6 of the cooling element 2, the water freezes or sublimates and accumulates as a layer of ice on the first surface 6. The accumulation of ice cannot be carried out indefinitely, and for this reason a detachment device 8 is used that is held so as to be movable relative to the cooling element 2. For example, the detachment device 8 comprises a scraping edge 10 that is in contact with the first surface 6. As a result of the scraping edge 10 moving along the first surface 6, the ice is scraped off. With continuous movement of the detachment device 8 along the first surface 6, said surface 6 can always remain free of ice so that an ideal cooling effect can always act on the water content of the gas 4, and consequently continuous, ideal, dehumidification of the gas 4 can be carried out.
Fig. 2 shows a more concrete exemplary embodiment of the apparatus 11. In this arrangement a cooling element 12 is designed as a hollow cylinder through which the gas 4 to be dried flows. With adequate cooling, the first surface 14, designed as an inside surface
-9-of the cooling element, is covered by ice, and the gas 4 is dried as it flows through the cooling element 12. To remove the ice layer on the first surface 14 a detachment device 16 is used that is rotatably held on an axis 18, wherein the axis 18 corresponds to the axis of extension of the cooling element 12 and consequently is arranged concentrically to the aforesaid. The drive of the detachment device 16 is implemented by a diagrammatically shown drive device 31 which by way of a shaft 33 is connected with the detachment device 16, wherein the shaft 33 extends over a greater height than does the cooling element 12, and consequently the inflow of the gas 4 to be dried is made possible.
In this arrangement the detachment device 16 comprises a spiral-shaped or helical edge 20 that continuously scrapes along the first surface 14 of the cooling element 12 when the detachment device 16 is rotating. In this manner continuous detachment of ice from the first surface 14 is carried out.
Preferably, the detachment device 16 comprises a helical turn arrangement that is sufficiently coarse to allow easy flow of the gas 4 through the apparatus, while at the same time, however, ice detachment can remain assured.
In the exemplary embodiment shown, the hollow-cylindrically-shaped cooling element 12 is enclosed by a further cylindrically-shaped body 22 that defines a gap 24 to the cooling element 12. A cooling medium could flow through this gap 24, which cooling medium by passing along a second surface 26 of the cooling element 12 results in cooling as a result of which the water content of the gas 4 freezes on the first surface 14.
A lower region 28 of the cooling element 12 comprises an outward-expanding shape which, for example as a reservoir, provides sufficient space for accumulated ice that has been detached from the first surface 14. Optionally, a corresponding aperture 30 can be provided through which the ice, or ice in the form of meltwater, which ice has been melted by exposure to external heat, is discharged. The outward-formed region 28 of the cooling element 12 could comprise a cover 32 that in the extension of the axis 18 comprises a cutout 34 that allows unimpeded flowing out of the gas 4.
In this arrangement the detachment device 16 comprises a spiral-shaped or helical edge 20 that continuously scrapes along the first surface 14 of the cooling element 12 when the detachment device 16 is rotating. In this manner continuous detachment of ice from the first surface 14 is carried out.
Preferably, the detachment device 16 comprises a helical turn arrangement that is sufficiently coarse to allow easy flow of the gas 4 through the apparatus, while at the same time, however, ice detachment can remain assured.
In the exemplary embodiment shown, the hollow-cylindrically-shaped cooling element 12 is enclosed by a further cylindrically-shaped body 22 that defines a gap 24 to the cooling element 12. A cooling medium could flow through this gap 24, which cooling medium by passing along a second surface 26 of the cooling element 12 results in cooling as a result of which the water content of the gas 4 freezes on the first surface 14.
A lower region 28 of the cooling element 12 comprises an outward-expanding shape which, for example as a reservoir, provides sufficient space for accumulated ice that has been detached from the first surface 14. Optionally, a corresponding aperture 30 can be provided through which the ice, or ice in the form of meltwater, which ice has been melted by exposure to external heat, is discharged. The outward-formed region 28 of the cooling element 12 could comprise a cover 32 that in the extension of the axis 18 comprises a cutout 34 that allows unimpeded flowing out of the gas 4.
- 10-Fig. 3a diagrammatically shows apparatus 11, which apparatus is connected with a cryogenic hydrogen tank 35 filled with liquid hydrogen. Liquid hydrogen enters the gap 24, cools the cooling element 12, and is returned to the tank 35 or is conveyed for use in a fuel cell or the like.
Fig. 3b diagrammatically shows a heat exchanger 37 that is cooled by ambient air 39. A
separate cooling circuit 41 connects the heat exchanger 37 with the apparatus so that direct introduction of ambient air can be prevented. After use in the heat exchanger 37 the ambient air 39 can be removed. As an alternative to this, in the apparatus ambient air can also flow directly through the gap 24.
Furthermore, Fig. 4 shows the essential steps of the method according to the invention. In the first instance a first surface of a cooling element is subjected 36 to a gas stream to be dried; by way of a thermal connection with a heat sink the cooling element is cooled 38 in order to, in this process, freeze the water vapor or water content contained in the gas so that the ice accumulates on the first surface. At the same time, subsequently or alternatingly, a detachment device on the first surface is moved 40 so that the ice that has accumulated on the first surface is removed. Optionally, removed ice is collected in a reservoir, and, furthermore optionally, is melted 42 by exposure to external heat. The ice collected in the reservoir can fall out of it or can be discharged 44 from it; likewise the ice that has optionally been melted by exposure to heat can be channeled out.
Finally, Fig. 5 shows an aircraft 46 comprising at least one fuel cell system 48 that feeds into fuel tanks 52 an exhaust gas containing water vapor through apparatus 50 in a dried state for rendering inert said fuel tanks 52.
In addition, it should be pointed out that "comprising" does not exclude other elements or steps, and "a" or "one" does not exclude a plural number. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments can also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.
Fig. 3b diagrammatically shows a heat exchanger 37 that is cooled by ambient air 39. A
separate cooling circuit 41 connects the heat exchanger 37 with the apparatus so that direct introduction of ambient air can be prevented. After use in the heat exchanger 37 the ambient air 39 can be removed. As an alternative to this, in the apparatus ambient air can also flow directly through the gap 24.
Furthermore, Fig. 4 shows the essential steps of the method according to the invention. In the first instance a first surface of a cooling element is subjected 36 to a gas stream to be dried; by way of a thermal connection with a heat sink the cooling element is cooled 38 in order to, in this process, freeze the water vapor or water content contained in the gas so that the ice accumulates on the first surface. At the same time, subsequently or alternatingly, a detachment device on the first surface is moved 40 so that the ice that has accumulated on the first surface is removed. Optionally, removed ice is collected in a reservoir, and, furthermore optionally, is melted 42 by exposure to external heat. The ice collected in the reservoir can fall out of it or can be discharged 44 from it; likewise the ice that has optionally been melted by exposure to heat can be channeled out.
Finally, Fig. 5 shows an aircraft 46 comprising at least one fuel cell system 48 that feeds into fuel tanks 52 an exhaust gas containing water vapor through apparatus 50 in a dried state for rendering inert said fuel tanks 52.
In addition, it should be pointed out that "comprising" does not exclude other elements or steps, and "a" or "one" does not exclude a plural number. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments can also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.
-11-LIST OF REFERENCE CHARACTERS
2 Cooling element 4 Gas 6 First surface 8 Detachment device Scraping edge 11 Apparatus
2 Cooling element 4 Gas 6 First surface 8 Detachment device Scraping edge 11 Apparatus
12 Cooling element 10 14 First surface 16 Detachment device 18 Axis Edge 22 Body 15 24 Gap 26 Second surface 28 Outwardly formed region Aperture 31 Drive device 20 32 Cover 33 Shaft 34 Cutout Cryogenic hydrogen tank 36 Subject to gas flow 25 37 Heat exchanger 38 Cooling the cooling element 39 Ambient air First surface 41 Separate cooling circuit 30 42 Melt 44 Discharge 46 Aircraft 48 Fuel cell system 50 Apparatus 52 Fuel tank
Claims (14)
1. Fuel cell system having an apparatus (11, 50) for drying of exhaust gas of the fuel cell system, comprising - at least one cooling element (2, 12) with at least one first surface (6, 14) and - at least one detachment device (8, 16), wherein the cooling element (2, 12) is designed to be thermally connected to a heat sink and to come into contact with the gas to be dried, which gas is flowing past, wherein the detachment device (8, 16) is movably held relative to the first surface (6, 14) and is designed to detach frozen water from the first surface (6, 14).
2. The fuel cell system of claim 1, wherein the detachment device (8, 16) comprises an edge (10, 20) for scraping off ice from the first surface (6, 14).
3. The fuel cell system of claim 1 or 2, further comprising a drive device (31) coupled to the detachment device (8, 16).
4. The fuel cell system of any one of the preceding claims, wherein the cooling element (2, 12) is a hollow body, wherein the first surface (6, 14) is an inside surface of the cooling element (2, 12).
5. The fuel cell system of any one of claims 1 to 3, wherein the cooling element (2, 12) is designed as a hollow cylinder at least in some sections, wherein the first surface (6, 14) is the inner lateral surface of the cooling element (2, 12).
6. The fuel cell system of claim 4 or 5, wherein the detachment device (8, 16) is spindle-shaped, with one of its outer spindle edges (20) being in contact with the inside surface of the cooling element (14), and is rotatably held on an axis (18) that is rigid relative to the cooling element (14).
7. The fuel cell system of any one of claims 4 to 6, further comprising a hollow body that encloses the cooling element (2, 14) so as to form a gap (24) for a fluid to flow through.
8. The fuel cell system of any one of claims 4 to 7, wherein the cooling element (12) on at least one end comprises an opening-out region (28).
9. The fuel cell system of any one of claims 1 to 8, wherein the heat sink is provided in the form of hydrogen from a cryogenic hydrogen tank (35).
10. A method for drying of exhaust gas of a fuel cell system, comprising the steps of:
- subjecting (36) a first surface (6, 14) of a cooling element (2, 12) to the exhaust gas of the fuel cell system, - cooling (38) the cooling element (2, 12), - moving a detachment device (8, 16) on the first surface (6, 14).
- subjecting (36) a first surface (6, 14) of a cooling element (2, 12) to the exhaust gas of the fuel cell system, - cooling (38) the cooling element (2, 12), - moving a detachment device (8, 16) on the first surface (6, 14).
11. The method of claim 10, further comprising the step of:
- discharging (44) the detached ice.
- discharging (44) the detached ice.
12. The method of claim 10 or 11, further comprising the step of:
- melting (42) the ice and discharging meltwater.
- melting (42) the ice and discharging meltwater.
13. An aircraft (46) with at least one fuel cell system (48) that is connected with at least one fuel tank (52) in such a manner that exhaust gas from the fuel cell system (48) renders the fuel tank (52) inert, and with at least one apparatus (11, 50) for drying the exhaust gas of the fuel cell system (48), comprising - at least one cooling element (2, 12) with at least one first surface (40) and - at least one detachment device (8, 16), wherein the cooling element (2, 12) is designed to be thermally connected to a heat sink and to come into contact with the exhaust of the fuel cell system flowing past, which exhaust gas is to be dried, - wherein the detachment device (8, 16) is movably held relative to the first surface (6, 14) and is equipped to detach frozen water from the first surface (6, 14).
14. The aircraft (46) of claim 13, further comprising a cryogenic hydrogen tank (35), wherein the heat sink is provided in the form of cryogenic hydrogen.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US25601509P | 2009-10-29 | 2009-10-29 | |
| US61/256,015 | 2009-10-29 | ||
| DE102009051212A DE102009051212B4 (en) | 2009-10-29 | 2009-10-29 | Fuel cell system with an apparatus for drying exhaust gas, method for drying exhaust gas of a fuel cell system and aircraft with such a fuel cell system |
| DE102009051212.8 | 2009-10-29 | ||
| PCT/EP2010/066034 WO2011051210A1 (en) | 2009-10-29 | 2010-10-25 | Fuel cell system and method for drying exhaust gas of a fuel cell system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2781710A1 true CA2781710A1 (en) | 2011-05-05 |
| CA2781710C CA2781710C (en) | 2017-01-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CA2781710A Expired - Fee Related CA2781710C (en) | 2009-10-29 | 2010-10-25 | Fuel cell system and method for drying of exhaust gas of a fuel cell system |
Country Status (6)
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| US (1) | US8978264B2 (en) |
| EP (1) | EP2494645B1 (en) |
| CN (1) | CN102687326B (en) |
| CA (1) | CA2781710C (en) |
| DE (1) | DE102009051212B4 (en) |
| WO (1) | WO2011051210A1 (en) |
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| DE102009051212B4 (en) * | 2009-10-29 | 2013-08-08 | Airbus Operations Gmbh | Fuel cell system with an apparatus for drying exhaust gas, method for drying exhaust gas of a fuel cell system and aircraft with such a fuel cell system |
| EP2675008B1 (en) * | 2012-06-15 | 2020-01-22 | Airbus Operations GmbH | Fuel cell system and method for operating a fuel cell system |
| DE102012222020B4 (en) | 2012-11-30 | 2022-03-31 | Airbus Operations Gmbh | System for supplying inert gas to an aircraft, method for supplying inert gas to an aircraft, use of a membrane and aircraft |
| DE102013105215A1 (en) | 2013-05-22 | 2014-11-27 | Airbus Operations Gmbh | Apparatus for cooling and dehumidifying gases, method for cooling and dehumidifying gases and vehicle with a fuel cell system and a device for cooling and dehumidifying fuel cell exhaust air |
| US10532311B2 (en) | 2017-06-30 | 2020-01-14 | Hamilton Sundstrand Corporation | Inert gas generation with dehumidification |
| DE102018128715A1 (en) * | 2018-11-15 | 2020-05-20 | Airbus Operations Gmbh | Cooling and gas dehumidifying system, means of transport and method for operating a cooling and gas dehumidifying system |
| CN112993329B (en) * | 2019-12-12 | 2022-03-15 | 中国科学院大连化学物理研究所 | Method for recycling reclaimed water in high-temperature tail gas of fuel cell |
| DE102021209603A1 (en) | 2021-09-01 | 2023-03-02 | Ekpo Fuel Cell Technologies Gmbh | Device for dehumidifying a fluid in a fuel cell system and fuel cell system |
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| US2129565A (en) * | 1937-08-31 | 1938-09-06 | William C Clay | Deicing attachment for airplane propellers |
| US2976935A (en) * | 1941-12-29 | 1961-03-28 | Edward F Andrews | Jet drive rotary wing system |
| US2423700A (en) * | 1943-06-16 | 1947-07-08 | Marquette Metal Products Co | Propeller blade |
| US2515341A (en) * | 1948-02-07 | 1950-07-18 | Paul T Giguere | Deicing attachment for motor vehicles |
| US3533395A (en) * | 1968-08-12 | 1970-10-13 | Stanray Corp | Aircraft deicer system and apparatus |
| JPH0636851B2 (en) * | 1990-03-27 | 1994-05-18 | 川崎重工業株式会社 | Disk type steam trap |
| KR980004460U (en) | 1996-06-04 | 1998-03-30 | Evaporator of refrigerator | |
| US6574979B2 (en) * | 2000-07-27 | 2003-06-10 | Fakieh Research & Development | Production of potable water and freshwater needs for human, animal and plants from hot and humid air |
| US20020112479A1 (en) * | 2001-01-09 | 2002-08-22 | Keefer Bowie G. | Power plant with energy recovery from fuel storage |
| FR2823533B1 (en) * | 2001-04-17 | 2003-08-08 | Eads Airbus Sa | AIR INLET HOOD FOR REACTION ENGINE, PROVIDED WITH DEFROSTING MEANS |
| WO2004015796A2 (en) * | 2002-04-17 | 2004-02-19 | Aerovironment, Inc. | Closed loop energy storage system |
| DE10251760A1 (en) * | 2002-11-05 | 2004-05-19 | Behr Gmbh & Co. | Air distribution device for distributing air in a motor vehicle's interior has a ventilating element for generating an air current linked to a flow channel and outlets leading into the interior |
| US7135245B2 (en) * | 2003-05-16 | 2006-11-14 | General Motors Corporation | Apparatus and method for stack temperature control |
| KR100534698B1 (en) | 2003-07-11 | 2005-12-07 | 현대자동차주식회사 | Fuel cell system |
| US20050235979A1 (en) * | 2004-04-22 | 2005-10-27 | Whittaker Thomas H | Windshield liquid wash heater |
| DE102004034870B4 (en) * | 2004-07-19 | 2007-08-09 | Liebherr-Aerospace Lindenberg Gmbh | A system for recovering water from an exhaust stream of a fuel cell of an aircraft and using the system in an aircraft |
| DE102005054885B4 (en) | 2005-11-17 | 2007-12-20 | Airbus Deutschland Gmbh | Safety system to reduce the risk of explosion of a fuel tank |
| US8394552B2 (en) * | 2006-09-19 | 2013-03-12 | Hamilton Sundstrand Corporation | Jet fuel based high pressure solid oxide fuel cell system |
| DE102007060428B3 (en) * | 2007-12-14 | 2009-05-07 | Airbus Deutschland Gmbh | Fuel cell system i.e. evaporation-cooled fuel cell system, for use in aircraft, has control unit controlling temperature of cell, where cooling agent is transferred into gaseous state in aggregate condition |
| JP2011516808A (en) * | 2008-03-19 | 2011-05-26 | ザ・トラスティーズ・オブ・ザ・ユニバーシティ・オブ・ペンシルバニア | System and method for generation of two-phase coolant and determination of its cooling capacity |
| DE102008050373B4 (en) * | 2008-10-02 | 2013-04-11 | Airbus Operations Gmbh | Safety system to reduce the risk of explosion of a fuel tank |
| US8436489B2 (en) * | 2009-06-29 | 2013-05-07 | Lightsail Energy, Inc. | Compressed air energy storage system utilizing two-phase flow to facilitate heat exchange |
| DE102009051212B4 (en) * | 2009-10-29 | 2013-08-08 | Airbus Operations Gmbh | Fuel cell system with an apparatus for drying exhaust gas, method for drying exhaust gas of a fuel cell system and aircraft with such a fuel cell system |
| DE102012002132A1 (en) * | 2012-02-03 | 2013-08-08 | Airbus Operations Gmbh | Anti-icing system for an aircraft and method of operating an anti-icing system |
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| WO2011051210A1 (en) | 2011-05-05 |
| US8978264B2 (en) | 2015-03-17 |
| DE102009051212B4 (en) | 2013-08-08 |
| EP2494645A1 (en) | 2012-09-05 |
| CA2781710C (en) | 2017-01-03 |
| CN102687326A (en) | 2012-09-19 |
| CN102687326B (en) | 2014-12-10 |
| DE102009051212A1 (en) | 2011-05-12 |
| EP2494645B1 (en) | 2015-12-16 |
| US20120261512A1 (en) | 2012-10-18 |
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